Accession Number : ADA306948
Title : Impact Resistance of Spar-Shell Composite Fan Blades.
Descriptive Note : Final rept.,
Corporate Author : UNITED TECHNOLOGIES CORP WINDSOR LOCKS CT HAMILTON STANDARD DIV
Personal Author(s) : Graff, J. ; Stoltze, L. ; Varholak, E. M.
PDF Url : ADA306948
Report Date : JUL 1973
Pagination or Media Count : 48
Abstract : Five composite spar-shell fan blades for a l.83 meter (6 feet) diameter fan stage were fabricated and tested in a whirling arm facility to evaluate foreign object damage (FOD) resistance. The blades were made by adhesively bonding boron-epoxy shells on titanium spars and then adhesively bonding an Inconel 625 sheath on the leading edge. The rotating blades were individually tested at a tip speed of 800 feet per second. Impacting media used were gravel, rivets, bolt, nut, ice balls, simulated birds, and a real bird. Incidence angles were typical of those which might be experienced by STOL aircraft. The tests showed that blades of the design tested in this program have satisfactory impact resistance to small objects such as gravel, rivets, nuts, bolts, and two inch diameter ice balls. The blades suffered nominal damage when impacted with one-pound birds (9 to 10 ounce slice size). However, the shell was removed from the spar for a larger slice size.
Descriptors : *FAN BLADES, *IMPACT STRENGTH, *EPOXY COMPOSITES, *FOREIGN OBJECT DAMAGE, *PROPELLER BLADES, *SHORT TAKEOFF AIRCRAFT, IMPACT TESTS, COMPOSITE STRUCTURES, SHELLS(STRUCTURAL FORMS), FLEXURAL STRENGTH, BIRD STRIKES, TITANIUM, LEADING EDGES, POLYURETHANE RESINS, BORON, ANGLE OF INCIDENCE, EPOXY RESINS, ADHESIVE BONDING, FOAM, TRAILING EDGES, SHEAR STRENGTH, SPARS, STRUCTURAL INTEGRITY.
Subject Categories : V/STOL
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE